CN107002700A - Compressor for exhaust-driven turbo-charger exhaust-gas turbo charger - Google Patents
Compressor for exhaust-driven turbo-charger exhaust-gas turbo charger Download PDFInfo
- Publication number
- CN107002700A CN107002700A CN201580064207.8A CN201580064207A CN107002700A CN 107002700 A CN107002700 A CN 107002700A CN 201580064207 A CN201580064207 A CN 201580064207A CN 107002700 A CN107002700 A CN 107002700A
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- Prior art keywords
- compressor
- flowing groove
- constituted
- inlet channel
- rotor chamber
- Prior art date
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- 238000003780 insertion Methods 0.000 claims description 40
- 230000037431 insertion Effects 0.000 claims description 40
- 239000000203 mixture Substances 0.000 claims description 3
- 239000007789 gas Substances 0.000 description 14
- 230000008901 benefit Effects 0.000 description 5
- 238000002485 combustion reaction Methods 0.000 description 5
- 239000002912 waste gas Substances 0.000 description 4
- 239000012530 fluid Substances 0.000 description 3
- 230000000087 stabilizing effect Effects 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 239000008186 active pharmaceutical agent Substances 0.000 description 2
- 230000004323 axial length Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 230000001976 improved effect Effects 0.000 description 2
- 238000001746 injection moulding Methods 0.000 description 2
- 238000005325 percolation Methods 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000004512 die casting Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
- F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
- F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/12—Improving ICE efficiencies
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Supercharger (AREA)
Abstract
The present invention relates to a kind of compressor, it has the air guiding portion section (3) that can be flowed, and the air guiding portion section has：Inlet channel (7)；The rotor chamber (5) constituted in inlet channel (7) downstream, the rotor chamber is used to accommodate compressor drum (4)；The helical duct (6) constituted in rotor chamber (5) downstream, wherein being constituted in air guiding portion section (3) in the transitional region for being connected inlet channel (7) with rotor chamber (5) has flowing groove (9), and wherein transitional region not only extends towards the direction of inlet channel (7) but also towards the direction of rotor chamber (5) on the air inlet edge of compressor drum (4), and wherein flowing groove (9) respectively axial direction the first length (L1) on and on radical length (RL) extension ground constitute have cross section (Q).According to the present invention, cross section (Q) is variable in the first length (L1) of axial direction.
Description
Technical field
The present invention relates to a kind of pressure for exhaust-driven turbo-charger exhaust-gas turbo charger of the type proposed in preamble of claim 1
Contracting machine.
Background technology
The working range of compressor in exhaust-driven turbo-charger exhaust-gas turbo charger is limited by stall margin and chocking limit, the surge
Border and chocking limit are the boundary lines for the comprehensive characteristics curve for representing compressor characteristics.Run in compressor adjacent to stall margin
When, the local stall zone by gauge is caused on the blade of compressor drum, the stall zone can result in flowing with the side of flowing
Pulsed to the mode of periodic transformation.Then, when volume flow less and less conveying passes through compressor, compressor is reached
Stall margin.
If the operating point of opposite compressor is moved in compressor comprehensive characteristics curve towards increasing volume flow,
Chocking limit can be so reached, the chocking limit is characterised by, volume flow stops rotor inlet at rotor inlet.
In order to expand the working range of compressor, comprehensive characteristics curve stabilizing measures are known, and the comprehensive characteristics are bent
Stall margin is not only moved in line stabilization measure but also mobile chocking limit is in favor of the working range of expansion.
Thus, for example a kind of comprehensive characteristics curve stabilizing measures are learnt from the A of open file US 4,212,585, according to
The ring of compressor drum entrance of the resultant curve stabilizing measures in the compressor housing of compressor in compressor drum is all
Upper composition has gap.Gap is constituted in specific length, and first slot ends in wherein gap are positioned at compressor drum and entered
The upstream at gas edge and second slot ends in gap are positioned at the downstream at compressor drum air inlet edge.In other words, gap
Axially extend beyond compressor drum air inlet edge.
The B1 of European patent document EP 0614014 are equally disclosed in the gap in compressor housing, and the gap is to surround
The mode of compressor drum is set.Gap is positioned at the upstream at the compressor drum air inlet edge of compressor drum, and in order to
Improved effect, the depth in gap is constituted with being approximately parallel to compressor drum ring circumferential edges.That is, be directed to realize with
The equidistant gap bottom surface of compressor drum ring circumferential edges.
The content of the invention
Using prior art as starting point, the present invention based on purpose be to provide and a kind of changing for exhaust-driven turbo-charger exhaust-gas turbo charger
The compressor entered.
The purpose is realized by the exhaust-driven turbo-charger exhaust-gas turbo charger of the feature with claim 1.The present invention's has favorably
And the favourable design of the improvement project of non-generic is provided in remaining claim.
It is proposed, according to the invention, that compressor has flowing groove in the transitional region for being connected rotor chamber with inlet channel,
The compressor includes the air guiding portion section that can be flowed, and the air guiding portion section has：Inlet channel；Under inlet channel
The rotor chamber constituted is swum, the rotor chamber is used to accommodate compressor drum；And the helical duct constituted in rotor chamber downstream.Cross
Region is crossed towards the direction of inlet channel and rotor chamber axially to extend.Flowing groove is respectively in the first length of axial direction and radially
Extend in length and with such as down cross-sectional, the cross section is variable in the first length of axial direction.
Due to the change of the cross section of flowing groove, the stream constituted in flowing groove is relative to constant horizontal stroke in the first length
Section changes in its fluid dynamic aspect of performance, wherein can realize further improve compressor in its stall margin and
Operation characteristic in terms of chocking limit.By means of the change of flowing groove geometry, the maximum matter of compressor drum can be influenceed
Measure the rise of flow.
In a design of the compressor according to the present invention, cross section is constituted in flowing groove towards inlet channel
Air inlet at there is first width, and have at the gas outlet that flowing groove is constituted towards compressor drum second wide
Degree, wherein the first width is more than or less than the second width.In other words, the cross section of flowing groove turns towards compressor in the axial direction
Son attenuates or increased.Advantage is, when protonatomic mass stream flows into inlet channel through flowing groove from rotor chamber, in other words in sub- matter
When amount flows back to stream, speed reduction can be relatively realized with the rotation direction of compressor drum and especially pressure is reduced.In addition,
Advantage when compressor is run in the scope away from stall margin is that the protonatomic mass for flowing through flowing groove is flowed through by additional favourable
Speed improve and pressure improve.
Another advantage is the manufacturability of compressor.Due to the taper of flowing groove, the shell part of compressor is with die casting
Method is cost-effectively manufactured.According to the configuration of shell part, the shell part energy single type or multi-piece type constitute.
Particularly advantageously, relative to the fluted shaft line of flowing groove, the taper constituted in the axial direction of flowing groove is at 0.5 °
Into 10 ° of number ranges.
In order to simply and cost-effectively manufacture air guiding portion section and flowing groove, the insertion that can be introduced into inlet channel
Ring is configured to flowing groove.Therefore, insertion ring can independently be manufactured with air guiding portion section.Due to the taper of flowing groove,
Insertion ring cost-effectively can be made with casting die.
According to the compressor of the present invention not only when compression ratio is low and when compression ratio is high with improved operation characteristic,
Wherein broadened on the whole because compressor comprehensive characteristics curve can be achieved in the movement of stall margin along the mass flow of compressor.
The efficiency of compressor can be raised on whole compressor comprehensive characteristics curve so that in compressor and internal combustion engine
The consumption that internal combustion engine can be achieved in combination is reduced.
The present invention other advantages, feature and details obtained from the description below preferred embodiment and according to
Accompanying drawing is obtained.The feature and combinations of features mentioned in the de-scription above and then mention in the description of the drawings and/or attached
The feature and combinations of features only shown in figure can not only with the combination that provides respectively and with other combinations or
Used in independent form, without departing from the scope of the present invention.
Brief description of the drawings
Accompanying drawing is shown：
Fig. 1 shows the stereogram of the compressor according to the present invention in the first embodiment, and it is in the profile of part
With insertion ring and stop sleeve；
Fig. 2 shows the side view of the insertion ring of the compressor according to the present invention according to Fig. 1；
Fig. 3 shows the profile of the flowing groove of the insertion ring according to Fig. 2；
Fig. 4 shows the local profile of the stop sleeve according to Fig. 1；
Fig. 5 shows the stereogram of the insertion ring according to Fig. 2；
Fig. 6 shows the stereogram of the insertion ring of the compressor according to the present invention in a second embodiment；
Fig. 7 shows the profilograph of the compressor according to Fig. 1；
Fig. 8 shows the stereogram of the compressor according to the present invention in the third embodiment, and it is in the profile of part
With insertion ring and stop sleeve.
Embodiment
In an exemplary first embodiment, the pressure according to the present invention of exhaust-driven turbo-charger exhaust-gas turbo charger 2 is constituted according to Fig. 1
Contracting machine 1.Compressor 1 has the shell part 3 of the form in the air guiding portion section that can be flowed, and is transported in exhaust-driven turbo-charger exhaust-gas turbo charger 2
During row, the shell part is flowed by fluid, generally by fresh air.Fresh air is generally used for the internal combustion not being shown specifically
Machine, with burning fuel.
Exhaust-driven turbo-charger exhaust-gas turbo charger 2 is associated with another shell part not being shown specifically, and another shell part is to support
The form of section constitutes and is used for the active wheel 17 for supporting exhaust-driven turbo-charger exhaust-gas turbo charger 2.Supporting section is positioned at exhaust gas turbine increasing
Between the waste gas flowed the guiding section not being shown specifically and air guiding portion section 3 of depressor 2.
Active wheel 17 has compressor drum 4 and the turbine that is not shown specifically, the compressor drum and turbine by means of
The axle not being shown specifically is torsionally connected.Compressor drum 4 is arranged in the rotor chamber 5 of air guiding portion section 3 for suction
Usual fresh air.The turbine not being shown specifically is rotatably received in another rotor not being shown specifically that waste gas guides section
In room.
When exhaust-driven turbo-charger exhaust-gas turbo charger 2 is run, turbine guides the waste gas of section to load and drive by percolation waste gas, wherein can
Enough turbines perform the rotational motion around pivot center 16 of active wheel 17.The rotational motion is delivered to compressor by means of axle
On rotor 4, the compressor drum is thus, it is possible to simultaneously perform rotational motion to realize the rotational motion of turbine.By means of pressure
Contracting machine rotor 4 and its rotational motion suction fresh air, the fresh air compress in air guiding portion section 3.
Air guiding portion section 3 has the helical duct 6 that can be flowed in the downstream of compressor drum room 5, by means of the spiral
Passage can deliver fluids to internal combustion engine.The inlet channel 7 for having air guiding portion section 3 is constituted in the upstream of rotor chamber 5, via described
Inlet channel can be by fresh air conveying to compressor drum 4.
In inlet channel 7, insertion ring 8 has been concentrically disposed with compressor drum 4, wherein insertion ring 8 with radially around
The mode of compressor drum 4 is constituted.Flowing groove 9, the substantially coaxial air to compressor drum 4 are provided with insertion ring 8
Conveying is feasible via the flowing groove.Flowing groove 9 in insertion ring 8 is formed to the bypass passageways of compressor drum 4, warp
It can realize that by the bypass passageways range of operation between stall margin and chocking limit of compressor 1 broadens.
Via the flowing groove 9 axially and radially extended along ring circumferential direction in insertion ring 8, the new of suction can be made
The protonatomic mass flow branching of fresh air, lead back and be incorporated to again percolation air guiding portion section 3 principal mass stream in.In chocking limit
Scope in when running, protonatomic mass stream is axially directed across the flowing groove 9 of insertion ring 8, but along with flowing into inlet channel 7
The principal mass stream identical direction guiding of flow of fresh air.
Insertion ring 8 is fixed in inlet channel 7 by means of stop sleeve 10.Stop sleeve 10 is in addition to its support function
There is diversion function as also illustrating.
Figure 2 illustrates the side view of insertion ring 8.Constitute and with multiple in ring Zhou Shangjun the single type of insertion ring 8
The flowing groove 9 of even distribution, the flowing groove is relative to the first angle α and phase that radially extend with restriction in insertion ring 8
Set, and especially prolonged on whole the first axial length L1 of insertion ring 8 with the second angle β limited for ring circumferential direction
Stretch.The stretching, extension inclined relative to ring circumferential direction of flowing groove 9 in insertion ring 8 is provided the advantage that：With flowing groove 9 only radially
The situation of extension is compared, and flowing groove 9 can have bigger cross-sectional area in the case of the wall thickness provided of insertion ring 8.
Thus, insertion ring 8 has ring portion section can partly flow, with ring diameter DS, and the ring portion section is more than the freedom of insertion ring 8
Ring diameter DR.
Each flowing groove 9 has the first width B1 and the second width B2, wherein the first width B1 is positioned at away from compressor
On first anchor ring 11 to be placed of rotor 4 and the second width B2 is positioned at towards second anchor ring to be placed of compressor drum 4
On 12.Thus, each flowing groove 9 is configured to its cross section Q from first in the way of extending on the first length L1 axially
The anchor ring of anchor ring 11 to the second 12 is tapered, referring to Fig. 3.Preferably, flowing groove it is axially extending on, flowing groove 9 is gradually
Attenuate or taper has 0.5 ° to 10 ° of cone angle on fluted shaft line 18.
Fig. 4 shows the local vertical section of stop sleeve 10, wherein the part shows the region towards insertion ring 8.Branch
Constitute and with the first interior diameter Dl1 and overall diameter DA1 support set 10 open column shapes of cylinder.Its towards insertion ring 8 end face
On 13, the stop sleeve has the second interior diameter Dl2, and second interior diameter is more than the first interior diameter Dl1.Second interior diameter
Dl2 is equivalent to ring diameter DS, referring to Fig. 2.Preferably, the second interior diameter Dl2 has 1.06 to 1.13 times of free ring diameter
DR.First interior diameter Dl1 preferably has 0.9 to 1.1 times of free ring diameter DR.
Using the second interior diameter Dl2 as starting point, the interior diameter Dl of stop sleeve 10 reduces directly in the second axial length L 2
To interior diameter Dl equivalent to the first interior diameter Dl1.Therefore ensure that, when flowing back to, protonatomic mass stream can be fully in flowing groove 9
Flowed out on whole radical length RL from flowing groove 9, because the air inlet face constituted on the first anchor ring 11 of flowing groove 9 is not by propping up
Support set cylinder 10 is directly covered.
By reducing interior diameter Dl, the protonatomic mass stream flowed back to flows back axially but only on the second length L2, because branch
The inwall of support set cylinder 10 forms flow resistance on radical length RL.Thus, stop sleeve 10 has diversion member 14.
In order to avoid flow separation, diversion member 14 is configured to the profile 15 in the axial direction with rounding.By means of
Second length L2 can realize very good flow behavior, and second length has 0.07 to 0.27 times of free ring diameter
DR.The profile 15 of rounding is preferably provided with the radius between 0.07 times and 0.13 times relative to free ring diameter DR.
Fig. 5 shows the three-dimensional view of the insertion ring 8 according to the present invention according to Fig. 1 to 3.
In fig. 6, it is illustrated that according to the insertion ring 8 of second embodiment.Insertion ring 8 is cost-effectively manufactured with aluminium injection moulding.
For example, insertion ring 8 also can in the injection molding method be manufactured by plastics.
Figure 7 illustrates the vertical section of the compressor 1 with insertion ring 8, the compressor has stop sleeve 10.Insertion
Ring 8 is positioned with one heart with compressor drum 4, and wherein insertion ring 8 is arranged in the region at compressor drum air inlet edge 19
Compressor drum 4 is incompletely surrounded on first length L1 of axial direction.
In order to fasten insertion ring 8 and in order to support or be fixed in inlet channel 7, stop sleeve 10 is positioned at inlet channel
In 7.The end face 13 that the first anchor ring of direction 11 of stop sleeve 10 is constituted sets described the in the way of contacting the first anchor ring 11
On one anchor ring 11.
Flowing groove 9 is orientated as on axially extending relative to compressor drum air inlet edge 19 so that axial is overlapping
Length LV is configured to the numerical value with 0.5 times of the first length L1.In other words, flowing groove 9 is with the first length L1's of its axial direction
One semi-surrounding compressor drum 4.Overlap length in the downstream of compressor drum air inlet edge 19, which is turned out to be, is matched with compressor
Insert region, the overlap length is located in the number range of the first length L1 equivalent to 0.1 to 0.8 times.
Figure 8 illustrates the 3rd embodiment of insertion ring 8, wherein with first embodiment differently, flowing groove 9 is in radial direction side
It is inclined upwards.According to the requirement for the internal combustion engine being connected with exhaust-driven turbo-charger exhaust-gas turbo charger 2 and desired runnability, for example in order to
Reduce and consume, the preferably inclination constituted on the contrary with the rotation direction of compressor drum 4 of flowing groove 9, but in order to big
Amplitude moves the stall margin of compressor 1, preferably inclination of the flowing groove 9 in the rotation direction of compressor 1.
Claims (9)
1. a kind of compressor, it has the air guiding portion section (3) that can be flowed, and the air guiding portion section has：Inlet channel
(7)；The rotor chamber (5) constituted in the inlet channel (7) downstream, the rotor chamber is used to accommodate compressor drum (4)；Institute
The helical duct (6) of rotor chamber (5) downstream composition is stated, wherein by the inlet channel in air guiding portion section (3)
(7) being constituted in the transitional region being connected with the rotor chamber (5) has a flowing groove (9), and wherein described transitional region not only court
The direction of the inlet channel (7) and towards the direction of the rotor chamber (5) on the air inlet edge of the compressor drum (4)
Extension, and the extension in the first length (L1) of axial direction and in the length (RL) of radial direction respectively of wherein described flowing groove (9)
Ground, which is constituted, cross section (Q),
Characterized in that,
The cross section (Q) is variable in axial first length (L1).
2. compressor according to claim 1,
Characterized in that,
The cross section (Q) is wide with first on the air inlet that the direction inlet channel (7) of the flowing groove (9) is constituted
Spend (B1), and there is the second width on the gas outlet of the direction compressor drum (4) composition of the flowing groove (9)
(B2), wherein first width (B1) is more than or less than second width (B2).
3. compressor according to claim 1 or 2,
Characterized in that,
Relative to the fluted shaft line (18) of the flowing groove (9), the flowing groove (9) has at 0.5 ° to 10 ° in the axial direction
Number range in taper.
4. the compressor according to any one of the claims,
Characterized in that,
Constituted in insertion ring (8) of the flowing groove (9) in it can be embedded in the inlet channel (7).
5. compressor according to claim 4,
Characterized in that,
The insertion ring (8) is fixed in the air guiding portion section (3) by means of locking device (10).
6. compressor according to claim 5,
Characterized in that,
The locking device (10) is constituted telescopicly.
7. the compressor according to claim 5 or 6,
Characterized in that,
The locking device (10) has diversion member (14) on the end regions that it is constituted towards the insertion ring (8).
8. compressor according to claim 7,
Characterized in that,
The diversion member (14) provides the groove constituted between the locking device (10) and the insertion ring (8), wherein institute
Locking device (10) is stated to be constituted in the way of contacting with the insertion ring (8).
9. the compressor according to any one of the claims,
Characterized in that,
The axially extending compressor drum air inlet edge (19) relative to the compressor drum (4) of the flowing groove (9) is fixed
Position into so that the flowing groove (9) compressor drum air inlet edge (19) downstream axial overlap length (LV)
Numerical value is located in following number range, and the number range corresponds to the 0.1 of first length (L1) of the flowing groove (9)
To 0.8 times of numerical value.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE102014117203.5A DE102014117203A1 (en) | 2014-11-25 | 2014-11-25 | Compressor for an exhaust gas turbocharger |
| DE102014117203.5 | 2014-11-25 | ||
| PCT/EP2015/002259 WO2016082916A1 (en) | 2014-11-25 | 2015-11-11 | Compressor for an exhaust-gas turbocharger |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107002700A true CN107002700A (en) | 2017-08-01 |
| CN107002700B CN107002700B (en) | 2020-02-11 |
Family
ID=54695655
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201580064207.8A Expired - Fee Related CN107002700B (en) | 2014-11-25 | 2015-11-11 | Compressor for an exhaust-gas turbocharger |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US10400789B2 (en) |
| JP (1) | JP6653326B2 (en) |
| CN (1) | CN107002700B (en) |
| DE (1) | DE102014117203A1 (en) |
| WO (1) | WO2016082916A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111094756A (en) * | 2017-09-14 | 2020-05-01 | 维特思科科技有限责任公司 | Radial compressor for a charging device of an internal combustion engine, charging device and lamella for a diaphragm and method for producing such a lamella |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| USD902961S1 (en) * | 2019-03-01 | 2020-11-24 | Savant Holdings LLC | Compressor housing |
| US10927702B1 (en) | 2019-03-30 | 2021-02-23 | Savant Holdings LLC | Turbocharger or turbocharger component |
| CN110005617A (en) * | 2019-04-19 | 2019-07-12 | 谱罗顿智控电子科技（浙江）有限公司 | A kind of intelligence centrifugal pump |
| WO2021070826A1 (en) * | 2019-10-09 | 2021-04-15 | 株式会社Ihi | Centrifugal compressor |
| USD900163S1 (en) * | 2020-02-20 | 2020-10-27 | Savant Holdings LLC | Compressor housing |
| CN117280124A (en) * | 2021-08-12 | 2023-12-22 | 株式会社Ihi | Centrifugal compressor and supercharger |
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| DE19920524C2 (en) * | 1999-05-05 | 2001-12-06 | Daimler Chrysler Ag | Centrifugal compressors |
| DE10105456A1 (en) * | 2001-02-07 | 2002-08-08 | Daimler Chrysler Ag | Compressors, in particular for an internal combustion engine |
| US7189059B2 (en) * | 2004-10-27 | 2007-03-13 | Honeywell International, Inc. | Compressor including an enhanced vaned shroud |
| DE102013113710B4 (en) * | 2013-12-09 | 2023-05-11 | Ihi Charging Systems International Gmbh | Bearing device for an exhaust gas turbocharger and exhaust gas turbocharger |
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2014
- 2014-11-25 DE DE102014117203.5A patent/DE102014117203A1/en active Pending
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2015
- 2015-11-11 WO PCT/EP2015/002259 patent/WO2016082916A1/en active Application Filing
- 2015-11-11 JP JP2017520946A patent/JP6653326B2/en active Active
- 2015-11-11 CN CN201580064207.8A patent/CN107002700B/en not_active Expired - Fee Related
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2017
- 2017-03-23 US US15/466,933 patent/US10400789B2/en not_active Expired - Fee Related
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| US4212585A (en) * | 1978-01-20 | 1980-07-15 | Northern Research And Engineering Corporation | Centrifugal compressor |
| US4781530A (en) * | 1986-07-28 | 1988-11-01 | Cummins Engine Company, Inc. | Compressor range improvement means |
| CN1096347A (en) * | 1993-03-04 | 1994-12-14 | Abb管理有限公司 | Has the centrifugal compressor that can make the stable casing that flows |
| US20020004004A1 (en) * | 2000-06-16 | 2002-01-10 | Peter Fledersbacher | Exhaust turbocharger for an internal combustion engine |
| EP1191231A2 (en) * | 2000-09-20 | 2002-03-27 | Hitachi, Ltd. | Turbo-type machines |
| DE102008039285A1 (en) * | 2008-08-22 | 2010-02-25 | Daimler Ag | Compressor for an internal combustion engine |
| CN103671265A (en) * | 2012-09-26 | 2014-03-26 | 博世马勒涡轮系统有限两合公司 | Centrifugal compressor for an exhaust gas turbocharger |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN111094756A (en) * | 2017-09-14 | 2020-05-01 | 维特思科科技有限责任公司 | Radial compressor for a charging device of an internal combustion engine, charging device and lamella for a diaphragm and method for producing such a lamella |
| CN111094756B (en) * | 2017-09-14 | 2022-04-08 | 维特思科科技有限责任公司 | Radial compressor, supercharging device and lamella and method for producing such lamellae |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107002700B (en) | 2020-02-11 |
| JP2017535710A (en) | 2017-11-30 |
| DE102014117203A1 (en) | 2016-05-25 |
| US20170191496A1 (en) | 2017-07-06 |
| WO2016082916A1 (en) | 2016-06-02 |
| US10400789B2 (en) | 2019-09-03 |
| JP6653326B2 (en) | 2020-02-26 |
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